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13 results on '"Simonson, M. R"'

1. Sun Microsystem's AutoClient and management of computer farms at BaBar

Author

Telnov, A. V., Luitz, S., Pavel, T. J., Saxton, O. H., and Simonson, M. R.

Subjects
Physics - Computational Physics, Physics - General Physics
Abstract

Modern HEP experiments require immense amounts of computing power. In the BaBar experiment at SLAC, most of it is provided by Solaris SPARC systems. AutoClient, a product of Sun Microsystems, was designed to make setting up and managing large numbers of Solaris systems more straightforward. AutoClient machines keep all filesystems, except swap, on a server and employ CacheFS to cache them onto a local disk, which makes them Field Replaceable Units with performance of stand-alone systems. We began exploring the technology in Summer 1998, and currently operate online, reconstruction, analysis and console AutoClient farms with the total number of nodes exceeding 400. Although the technology has been available since 1995, it has not been widely used, and the available documentation does not adequately cover many important details of AutoClient installation and management. This paper discusses various aspects of our experience with AutoClient, including tips and tricks, performance and maintainability, scalability and server requirements, existing problems and possible future enhancements., Comment: This paper has been submitted to Proceedings of the Conference on Computing in High Energy and Nuclear Physics (CHEP 2000), February 7-11, Padova, Italy. 4 pages; LaTeX2e; requires the CHEP 2000 class file c2k.cls

Published
2000

2. Analytical and experimental investigation of flow fields of annular jets with and without swirling flow

Author

Simonson, M. R, Smith, E. G, and Uhl, W. R

Subjects
Fluid Mechanics And Heat Transfer
Abstract

Analytical and experimental studies were performed to define the flowfield of annular jets, with and, without swirling flow. The analytical model treated configurations with variations of flow angularities, radius ratio, and swirl distributions. Swirl distributions characteristic of stator vanes and rotor blade rows, where the total pressure and swirl distributions are related were incorporated in the mathematical model. The experimental studies included tests of eleven nozzle models, both with and, without swirling exhaust flow. Flowfield surveys were obtained and used for comparison with the analytical model. This comparison of experimental and analytical studies served as the basis for evaluation of several empirical constants as required for application of the analysis to the general flow configuration. The analytical model developed during these studies is applicable to the evaluation of the flowfield and overall performance of the exhaust of statorless lift fan systems that contain various levels of exhaust swirl.

Published
1974

3. Reduction of fan noise: A concept

Author

Simonson, M. R

Subjects
Mechanics
Abstract

Acoustic materials strategically located within or near noise sources are effective for noise abatement on wing mounted lift fans, nozzles, engines and other noise sources. Panels are straightforward and easily adaptable to situations outside of aircraft technology.

Published
1972

4. Design of a miniature hydrogen fueled gas turbine engine

Author

Burnett, M, Lopiccolo, R. C, Simonson, M. R, Serovy, G. K, Okiishi, T. H, Miller, M. J, and Sisto, F

Subjects
Propulsion Systems
Abstract

The design, development, and delivery of a miniature hydrogen-fueled gas turbine engine are discussed. The engine was to be sized to approximate a scaled-down lift engine such as the teledyne CAE model 376. As a result, the engine design emerged as a 445N(100 lb.)-thrust engine flowing 0.86 kg (1.9 lbs.) air/sec. A 4-stage compressor was designed at a 4.0 to 1 pressure ratio for the above conditions. The compressor tip diameter was 9.14 cm (3.60 in.). To improve overall engine performance, another compressor with a 4.75 to 1 pressure ratio at the same tip diameter was designed. A matching turbine for each compressor was also designed. The turbine tip diameter was 10.16 cm (4.0 in.). A combustion chamber was designed, built, and tested for this engine. A preliminary design of the mechanical rotating parts also was completed and is discussed. Three exhaust nozzle designs are presented.

Published
1973

8. Transonic Fan/Compressor Rotor Design Study. Volume 6

Author

GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP, Parker, D. E., Simonson, M. R., GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP, Parker, D. E., and Simonson, M. R.

Abstract

This report describes the aerodynamic design of a series of five transonic rotors all parametrically related to a baseline design documented in Technical Report AFAPL-TR-79-2078. Each of the five designs deviate from the base line, in so far as practical, by a variation of parameter only. The parametric variations are specified at the rotor tip. The original hub characteristics were preserved to the maximum extent practical. The varied parameter was adjusted along the span., See also Volume 5, ADB069405

Published
1982

9. Transonic Fan/Compressor Rotor Design Study. Volume 1

Author

GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP, Parker, D. E., Simonson, M. R., GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP, Parker, D. E., and Simonson, M. R.

Abstract

Volumes I through VI of this report describes the aerodynamic design of a series of five transonic rotors all parametrically related to a baseline design documented in Technical Report AFAPL-TR-79-2078. Each of the five designs deviate from the base line, in so far as practical, by a variation of one parameter only. The parametric variations are specified at the rotor tip. The original hub characteristics were preserved to the maximum extent practical. The varied parameter was adjusted along the span. The report contains six volumes. Volume I contains primarily introduction and summary information plus details of a data match analysis of the base design. Volumes II through VI each contain design details for one of the series of five rotors., See also Volume 2, ADB069402

Published
1982

10. Transonic Fan/Compressor Rotor Design Study. Volume 4

Author

GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP, Parker, D. E., Simonson, M. R., GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP, Parker, D. E., and Simonson, M. R.

Abstract

Volumes I through VI of this report describes the aerodynamic design of a series of five transonic rotors all parametrically related to a baseline design documented in Technical Report AFAPL-TR-79-2078. Each of the five designs deviate from the base line, in so far as practical, by a variation of one parameter only. The parametric variations are specified at the rotor tip. This volume describes the aerodynamic design details of the Phase III rotor. The Phase III rotor was designed to have a steeper average suction surface angle in the supersonic region ahead of the shock than the baseline rotor. This results in a smaller cascade throat area in the outer 80% of the blade than the baseline rotor. The hub region was kept essentially the same as the baseline rotor., See also Volume 5, ADB069405 and Rept. no. AFAPL-TR-79-2078, ADB042609

Published
1982

11. Transonic Fan/Compressor Rotor Design Study. Volume 5

Author

GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP, Parker, D. E., Simonson, M. R., GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP, Parker, D. E., and Simonson, M. R.

Abstract

This volume describes the aerodynamic design details of the Phase IV rotor. The Phase IV rotor as well as the Phase III rotor described in detail in Volume IV of this report, was designed to have a steeper average suction surface angle in the supersonic region ahead of the shock than the baseline rotor. This results in a smaller cascade throat area in the outer 80% of the blade than the baseline rotor. While the throat areas of the Phase III and Phase IV rotors are essentially the same, the Phase IV blade has some what less external compression and some what more internal compression. As a result, the Phase IV blade has less suction surface (and meanline) curvatures in the region of the cascade mouth than does the Phase III rotor. The hub region was kept essentially the same as the baseline rotor. The location of maximum airfoil thickness is 70% of length at the tip and 56% at the hub which is the same as the baseline rotor., See also Volume 2, ADB069402 and Rept. no. AFAPL-TR-79-2078, ADB042609

Published
1982

12. Transonic Fan/Compressor Rotor Design Study. Volume 3

Author

GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP, Parker, D. E., Simonson, M. R., GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP, Parker, D. E., and Simonson, M. R.

Abstract

Volumes I through VI of this report describes the aerodynamic design of a series of five transonic rotors all parametrically related to a baseline design documented in Technical Report AFAPL-TR-79-2078. Each of the five designs deviate from the base line, in so far as practical, by a variation of one parameter only. The parametric variations are specified at the rotor tip. The original hub characteristics were preserved to the maximum extent practical. The varied parameter was adjusted along the span. This volume describes the aerodynamic design details of the Phase II rotor. The Phase II rotor has the tip airfoil maximum thickness located at 55% of meanline length as compared with 70% for the baseline rotor. The location of maximum thickness varied linearly with stream function to 56% of meanline length at the hub, which is the same as the baseline rotor., See also Volume 4, ADB069404 and Rept. no. AFAPL-TR-79-2078, ADB042609

Published
1982

13. Transonic Fan/Compressor Rotor Design Study. Volume 2

Author

GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP, Parker, D. E., Simonson, M. R., GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP, Parker, D. E., and Simonson, M. R.

Abstract

Volumes I through VI of this report describes the aerodynamic design of a series of five transonic rotors all parametrically related to a baseline design documented in Technical Report AFAPL-TR-79-2078. Each of the five designs deviate from the baseline, in so far as practical, by a variation of one parameter only. The parametric variations are specified at the rotor tip. This volume describes the aerodynamic design details of the Phase I Rotor. The Phase I rotor has the tip airfoil maximum thickness located at 40% of meanline length as compared with 70% for the baseline rotor. The location of maximum thickness varied linearly with radius to 56% of the meanline length at the hub, which is the same as the baseline rotor., See also Volume 3, ADB069403 and Rept. no. AFAPL-TR-79-2078, ADB042609

Published
1982

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